EASA AD No.: 20 14

- 0202 R1

TE.CAP.0011 0

- 00 4 © European Aviation Safety Agency. All rights reserved. 1 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No

. : 20 14

- 0202 R1

Date: 19 September 2014

Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the European Community, its Member States and of the European third countries that participate in the activities of EASA under Article 66 of that Regulation.

This AD is issued in accordance with EU 748/2012, Part 21.A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may ope rate an aircraft to which an AD applies, except in accordance with the requ irements of that AD, unless otherwise specified by the Agency [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemption]

. 

### Design Approval Holder’s Name:
AIRBUS Type/Model designation(s):
A300

- 600 and A310 aeroplanes

TCDS Number: EASA.A.172

F oreign AD: Not applicable

R evision : This AD revises EASA AD 2014

- 0202 dated 11 September 2014.



### ATA 53 Fuselage

– Door Frames Holes

– Inspection

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A300 B4

- 60 3, A300B4

- 605R, A300B4

- 622R, A310

- 30 4, A310

- 308, A310

- 324 and A310

- 325 aeroplanes, all m anufacturer s erial n umbers in post

modification ( MOD ) 06924 configuration, except MSN 464, 477, 479, 481,482, 483, 484 and 488. Note: MSN 464, 477,479, 481, 482, 483, 484 and 488 partially embodied MOD 06924 by means of modification proposal D05902.

Reason: During the preparation phase for conversion of an A300

- 600 aeroplane from passenger to freighter configuration , a crack was detected on door frame (FR) 73A, between stringer (STRG) 24 and STRG 25.
DGAC France had issued AD 1999

- 013

- 276R1 to require inspections at FR 73A in accordance with the instructions of Airbus Service Bulletin (SB) A310

- 53

- 2107 or SB A300

- 53

- 6116, as applicable. However, the new crack was found in an area not cov ered by the existing inspection and is therefore addr essed by this new AD. ( DGAC France AD 1999

- 013

- 276R1 remains in place).

Further investigations identified that, on A300

- 600 aeroplanes , the areas at FR 56A and FR 57A have the same design and material as at FR 73A

. This condition, if not detected and corrected
, could affect the structural integrity of the airframe.

For the reason s describe d above, this AD requires repetitive inspection s of the rivet head s of the seal retainer run out holes to detect crack s and , depending on findings, accomplishment of corrective actions

.EASA AD No.: 20 14

- 0202 R1

TE.CAP.0011 0

- 00 4 © European Aviation Safety Agency. All rights reserved. 2 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. Even though no crack has been identified at FR 56A and FR 57A, as a preventive measure , the inspection is extended to these areas. On A310 aeroplanes, only the area at FR 73A needs to be inspected

. This AD is revised to reduce the applicability to aeroplanes in post

- MOD 06924 configuration.

Effective Date: 25 September 2014

Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously: (1) With in the compliance time as defined in T able 1 of this AD, as applicable, and
, thereafter
, at interval s not to exceed 7 500 flight cycles (FC), accomplish a High Frequency Eddy Current ( HFEC ) inspection around the rivet head s of the seal retainer run out holes on A300

- 600 aeroplanes at FR 56A, FR 57A and FR 73A
, left

- hand ( LH ) and right

- hand ( RH ) side s , and on A310 aeroplanes at FR 73A
, LH and RH side s , in accordance with the instructions of Airbus SB A310

- 53

- 2138 or Airbus SB A300

- 53

- 6175, as applicable.

Table 1

– Compliance Time for In spection

Compliance Time (whichever occurs later, A or B )

A Before exceeding 32 000 FC since aeroplane first flight

B Within 36 m onths after the effective date of this AD
, without

exceed ing 36 000 FC since aeroplane first flight

(2) If, during any inspection as required by paragraph (1) of this AD, a crack is found, before next flight, contact Airbus to obtain a Repair Design Approval Sheet (RDAS) and accomplish that repair accordingly, including post

- repair follow

- on action(s), if an y are specified in that RDAS. (3) Accomplishment of a repair on an aeroplane, as required by paragraph ( 2 ) of this AD, does not constitute terminating action for the repetitive inspections as required by paragraph (1) of this AD for that aeroplane, unless the RDAS indicates otherwise

.

Ref. Public ations: Airbus SB A310

- 53

- 2138 original issue dated 28 May 2014

. Airbus SB A300

- 53

- 6175 original issue dated 28 May 2014

. The u se of later approved revisions of these documents is acceptable for compliance with the requirements of this AD.

Remarks: 1. If requested and appropriately substantiated, EASA can approve Alternative Methods of Compliance for this AD.

2. The original issue of this AD was posted on 30 July 2014 as PAD 14

- 124 for consultation until 27 August 2014

. The Comment Response Document can be found at http://ad.easa.europa.eu

. 3. Enquiries regarding this AD should be referred to the Safety Information Section, Certification Directorate, EASA. E

- mail: ADs@easa.europa.eu

. 4. For any question concerning the technical content of the requirements in this AD, please contact: AIRBUS SAS

– EIAW (Airworthiness Office), E

- mail: continued.airworthiness

- wb.external@airbus.com

.